GB1137630A - Improvements in axial flow gas turbines - Google Patents
Improvements in axial flow gas turbinesInfo
- Publication number
- GB1137630A GB1137630A GB4192466A GB4192466A GB1137630A GB 1137630 A GB1137630 A GB 1137630A GB 4192466 A GB4192466 A GB 4192466A GB 4192466 A GB4192466 A GB 4192466A GB 1137630 A GB1137630 A GB 1137630A
- Authority
- GB
- United Kingdom
- Prior art keywords
- plate
- shield
- bolts
- blades
- discs
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1,137,630. Gas turbine rotor cooling. GENERAL ELECTRIC CO. Sept. 20, 1966, No. 41924/66. Headings F1G and F1T. The bladed turbine rotor discs 19, 22 in a gas turbine engine are connected by a cylindrical heat shielding member 34 having integral annular sealing plates 40, 45 attached to the respective discs by bolts (41, 46), Figs. 2 to 4 (not shown), passing through holes 58, 52 in the plates. An integral disc 33 stiffens the shield 34. Cooling air is supplied from the engine compressor to the chamber 60 defined by the shield, some of the air then flowing through those holes 58 unoccupied by bolts to an annular channel 55 in plate 40 and thence to passages 57 in the blades 18. The remainder of the air flows in similar manner to passages 54 in the blades 21. The annular channel in plate 45 is bounded on its radially outer side by an annular sealing surface 45' offset from the remainder of the plate to form an axial gap 50 between the plate and the blade roots 21'. The gap 50 and the flexibility of the plate 45 enables axial expansion of the shield 34 to be accommodated. Sealing ribs 66 on the shield co-operate with a honeycomb seal 67 on the stator blades 20. The main driving connection between the discs 19, 22 is through a torque ring 25 and tie bolts (28).
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4192466A GB1137630A (en) | 1966-09-20 | 1966-09-20 | Improvements in axial flow gas turbines |
FR78055A FR1494654A (en) | 1966-09-20 | 1966-09-28 | Rotor assembly for gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4192466A GB1137630A (en) | 1966-09-20 | 1966-09-20 | Improvements in axial flow gas turbines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1137630A true GB1137630A (en) | 1968-12-27 |
Family
ID=10421996
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4192466A Expired GB1137630A (en) | 1966-09-20 | 1966-09-20 | Improvements in axial flow gas turbines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1137630A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2015200242A (en) * | 2014-04-09 | 2015-11-12 | 株式会社東芝 | Axial flow turbine |
US9441639B2 (en) | 2013-05-13 | 2016-09-13 | General Electric Company | Compressor rotor heat shield |
US9453427B2 (en) | 2013-10-30 | 2016-09-27 | General Electric Company | Systems and methods for purging an aft joint of a last stage wheel |
EP3348786A1 (en) * | 2017-01-17 | 2018-07-18 | Siemens Aktiengesellschaft | Rotor with ring cover and seal plates |
CN111828108A (en) * | 2020-07-24 | 2020-10-27 | 中国科学院工程热物理研究所 | Cover plate disc structure for engine turbine disc prerotation system |
CN113623014A (en) * | 2021-07-22 | 2021-11-09 | 西安交通大学 | Gas turbine blade-wheel disc combined cooling structure |
-
1966
- 1966-09-20 GB GB4192466A patent/GB1137630A/en not_active Expired
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9441639B2 (en) | 2013-05-13 | 2016-09-13 | General Electric Company | Compressor rotor heat shield |
US9453427B2 (en) | 2013-10-30 | 2016-09-27 | General Electric Company | Systems and methods for purging an aft joint of a last stage wheel |
JP2015200242A (en) * | 2014-04-09 | 2015-11-12 | 株式会社東芝 | Axial flow turbine |
EP3348786A1 (en) * | 2017-01-17 | 2018-07-18 | Siemens Aktiengesellschaft | Rotor with ring cover and seal plates |
CN111828108A (en) * | 2020-07-24 | 2020-10-27 | 中国科学院工程热物理研究所 | Cover plate disc structure for engine turbine disc prerotation system |
CN111828108B (en) * | 2020-07-24 | 2023-02-21 | 中国科学院工程热物理研究所 | Cover plate disc structure for engine turbine disc prerotation system |
CN113623014A (en) * | 2021-07-22 | 2021-11-09 | 西安交通大学 | Gas turbine blade-wheel disc combined cooling structure |
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